Turbine.



TUBBINE.

APPLIOATION PILBD APR. 3, 1908.

Patented Mar. 16, 1909.

3 SEEE'IS-SHEET 1.

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A. J. B. LG.

TURBINE.

APPLIOATION FILED .APK. 3, 1908.

Patenfed Mar. 16, 1909. 3 SHEETs-SHEET 3.

jne/6177237 915,o99. &1% *4 Fig CO resss ANNIBAL JEAN BAPTISTE LEG, orLONDON, ENGLAND.

TURB INE No. 915,o99.

Specification of Letters Patent.

Patented. March 16, 1909.

Application filed April 3, 1908. Serial No. &25,004.

To all whom 'it may concerns Be it known that I, ANNIBAL J EAN BAP-TISTE LG, a citizen of the French Republic, of 45 Lofting road,Barnsbury, London, England, engineer, have invented a certain new anduseful Improvement in Turbines, of which the following is a full, clear,and exact description, and for which I have applied for Letters Patentin Great Britain, No. 7,955, dated April 5, 1907.

This invention relates to certain improvements in turbines, whethertheacting fluid be of an eXpanding nature or of a non-eX- panding one, andit has for its purpose to utilize to the best advantage the energycontained in the fluid used, and to avoid back pressure.

The invention has reference to the type of turbine in which the fluideXerts a ressure upon moving piston-vanes attachec to the rotor, thispressure being maintained in the forward direction by the incomingtangential jet of fluid. This jet is of the full width of the chamberinto which it plays and while maintaining the forward pressure, itprevents any escape of fluid in the reverse direction; the portion ofthe chamber to the rear of the jet is in fact open to eXhaust by a portsituatecl behind the inlet port. Each pistonvane is thus exposed uponone face to the pressure maintained by the jet of fluid and upon theother face to the pressure of the eXhaust. The driving eflort isobtained by the diflerence between these pressures as in a reciprocatingengine; this distinguishes the present type of turbine from impact,impulse and reaction turbines.

The present invention consists in certain improvements in turbines ofthis type, for the purposes of reducing the back-pressure upon thepiston-vanes and of rendering the turbine more suitable for use as acompound or as a multi-stage machine.

This turbine consists of two principal parts, the statonary part whichcontains the means of admission of the fluid (which said means may be inthe shape of eXpanding nozzles or of slots with a view to cause anincrease of velocity of the fluid), the means of eXhaust and annularrecesses to form chambers; and the other part is the rotor or rotatingpart or disk carrying the one or more piston-vanes, or ressure receivingarrangements, and this disk is fixed on the shaft.

The invention utilizes a fluid jet coming from for example a nozzle,this jet playing more or less tangentially or obliquely to the directionof rotation into a chamber. This chamber is formed by an annular recessin the stationary part, and one side of the rotating part. The aforesaidjet plays against and provides the fluid which presses against apiston-vane or pressure-receivng arrangement. This pressure receivingarrangement forms part of the rotating portion and is free r to move inthe above-named annular recess, and the velocity of said jet of fluidwhich is of the whole width of the chamber into which it plays, causesit to form a kind of wall which separates the fluid in front of it fromany fluid at the back of it, so that all the energy of the incoming jetacts in advance of said jet. The invention also comprises, incombination with the foregoing arrangement to aford a steam or gas wall,a means of eXhaust placed at any point close to the back part of thesaid jet in such a way as not to disturb the jet's full action andplaced at any one of the sides of the stationary part of the chamberinto which the jet plays, eX- cepting the nozzle side that is the sidethe jet comes from. The reason for this arrangement of the eXhaust is toallow by its direction the outgoing fluid to retain and continue its ownline of motion (instead of being bent back on itself) which thus remainspractically the same as the direction of its working in the chamber, andalso in the case of gradual eXpansion of fluid, as Where the engine iscompound, this direction of eXhaust enables the exhaustng arrangement ofone chamber to form or become the means of inlet into the next largerchamber.

Upon the accompanying drawings I have illustrated my invention asapplied to multistage steam turbines. 4

Figure l is an end elevation of a turbine, the upper part being incentral section. Fig. 2 is a sectional elevation at right angles toFig. 1. Fig. 3 is a sectional elevation of a modified turbine in whichthe fluid passes through annular chambers arranged in aXial succession.Figs. 4 and 5 are eXplanatory diagrams.

In Figs. 1 and 2, the turbine casing a is formed With a jacket I) towhich the steam is admitted. The nozzles c receive steam from thisjacket and deliver it in a tangential direction against the first seriesof piston vanes d rotating in the first annular chamber e.

llO

The internal wall of this chamber e consists of a ring f integral withthe casing a and having a number of passages g thcrethro'ugh. Thesepassages g form a means of exhaust for the chamber e and also a means ofdelivery for a second chamber h, into which the steam is directedtangentially to the piston-vanes i rotating therein. The position of thepassages g in the ring f is such that the piston uncovers the passagefor eXha'ust just before it reaches the incoming jet from the nozzle c,while the passage lies behind the line of the nozzle so that the area ofhigh pressure in front of the nozzle is always separated from 13 thearea of low pressure at the eXhaust passage by the dividing wallconstituted by the incoming steam. In a similar manner the secondchamber h eXhausts through passages 7' in another ring ?c to a thirdannular chamber Z, the steam being directed again tangentially againstthe pistons m. From this chamber the steam exhausts through ports n to aconduit o leading to the condenser. A fourth annular chamber p is shownfor the purposes of reversing, and to effect this, steam is introducedto a central chamber g and delivered through nozzles r againstpiston-vanes s. For the sake of clearness I have shown separateeXhaust-ports n for the reversing chamber. The eXhaust from this chambermay however be led through passages inthe ring t, similar to thepassages g, y', and directed against the pistons m and so to the eXhaustat n as before, or the reversing steam may be carried one or more stagesfurther into the chambers h, e, and thence exhausted, the conimunicatingpassages being suitably formed for this purpose. The piston-vanes d, i,m are mounted upon a disk 40 u, secured to a shaft 7), and a similarseries of chambers and pistons is arranged upon the other side of thedisk, one series only being shown in section in Fig. 2. The steampressure upon the one side of the disk is thus caused to balance thatupon the other side, so that no end-thrust results. Where, as in aturbine for driving a screw propeller, endthrust is advantageous, onlyone series of pistons and chambers may be employed. It o -will beunderstood that the number of annular chambers will be determined by therequirements of each individual case. Between the disk and thestationary parts, a steam packing is introduced' consisting ofconcentric grooves and fillets to prevent leakage.

In Fig. 3 is shown a modified construction in which the annular chambersare no longer placed eoncentrically one with another,

but in different planes in aXial succession along the shaft. In aturbine of this type, as in the case of the reversing nozzles 7" of thepreviously-described turbine, the noz- Zles cannot conveniently bearranged to deliver tangentially into the chambers.

They are therefore placed as shown at a slight inclination which is keptas small as circumstances will allow. The steam is admitted to asteam-chest ?7 within which the nozzles c are located, and assessuccessively as before through chamlers e, h, Z and a fourth chamber 10to the eXhaust conduit 0 leading to the condenser. Each of theintermediate rings f, k, t is formed with packing grooves and filletscorresponding With fillets and grooves upon the rotor a; similar packingis rovided at each eXtremity of the rotor. T e eXhaust-inlet passages inthis turbine are formed in a similar manner to those in the previousconstruction; the machine may therefore be reversed by passing steam ina contrary direction, for inst ance by admitting it to the exhaustconduit and exhausting at one of the early stages, say chamber h. Thequantity of steam passing will depend upon the size of the chamber fromwhich the exhaust takes place; to obtain additional power in reversingit may therefore be necessary to release a portion of the steam at anintermediate stage. Similarly, to obtain additional torque at startingor other times, additional steam of high pressure may be admitted directto all or any of the stages. suitable slide or other valves for theseurposes are arranged in the turbine as required.

Fig. 4 shows in section a form of blade, which may be employed in thistype of turbine to obviate end-thrust. In this blade, the two internalfaces of the blade are so designed that their geometrical 1projectionsparallel to the shaft are equa; the two longitudinal Components of thepressures (acting upon the blades as shown by the arrows) wll thereforeneutralize one another and the resultant pressure will be purelytangential. As previously stated, however, with reference to the formertype, it may be advantageous in certain cases to allow of end-thrustupon the rotor; in such cases one or other of the internal faces of theblade will be reduced according to the end-thrust required.

Fig. 5 shows diagrammatically in its simplest form the principle of thepresent invention. The chamber e receives steam for one of its sectionsat A in the direction shown, this being approximately tangential to tltepath of the pisten. The eXhaust takes place from the preceding sectioneither to condenser or to a second stage in either direction B,direction C, or direction D. In any case the exhaust passage is notimmediately opposite to the jet A but is some distance behind (againstthe direction of the piston) so that a wall of steam is formed toseparate the high pressure area in front of the jet from the lowpressure area at the eXhaust passage.

The piston-vanes or pressure-receiving 130 devices may be provided withholes or apertures passing through them 'and forming nozzles so as tofavor velocity of the fluid and either create a vacuum at the front ofthe piston-blade or pressure-receiving arrangement, or to counter fluidpressure against it, and' also as a means to favor a slower speed of theengine without loss of power;

I am aware that in rotary engines having a radial flow, two similarunits have been arranged symmetrcally upon the shaft for the purpose ofbalancing end-thrust and to such arrangement I make no claim, but

Having thus described my invention, what I claim as such and desire tosecure by Letters Patent isz- 1. A turbine comprising a stator, achamber in said stator, walls to said chamber, a rotor, widely separatedpiston Vanes upon said motor, said Vanes traveling in said chamber, aninlet nozzle arranged to discharge through one wall of said ehamber, andan exhaust passage in a second wall of the chamber and arrangedimmediately to the rear of the inlet nozzle whereby the fluid admittedthrough said nozzle' forms a separating wall which prevents the passageto eX- haust of fluid from said ehamber in advanee of said nozzle inrelation to the direction of rotation.

2. A turbine, cemprising a stator, a chamber in said stator, walls tosaid ehamber, a rotor, widely separated piston-Vanes upon said rotor,said piston-vanes traveling in said ehamber, a nozzle in a wall of saidchamber adapted to deliver fluid into the chamber, and an eXhaustpassage in a second wall of said chamber in rear of the nozzle wherebythe fluid entering the chamber forms a separating wall which divides thechamber into a forward portion of high pressure and a rearward portionwhich is open to the exhaust passage.

3. A turbine, comprising a stator, a chamber in *said stator, walls tosaid ehamber, a rotor, piston vanes upon said rotor, said piston-vanesbeing widely separated and traveling in said chamber, a nozzle in a wallof said chamber adaptcd to admit fluid into the ehamber, and an exhaustpassage in a second wall of said chamber, said eXhaust lying immediatelyto rear of said nozzle, said nozzle adapted to admit a jet which issubstantially the full width of the chamber whereby the fluid forms aseparating wall which prevents the passage to eXhaust of fluid fronisaid chamber in advance of said nozzle in relation to the direction ofrotation.

4. A turbine, comprising a stator, a chamber therein, walls to saidchamber, a rotor, piston-vanes upon said rotor, said pistenvanes beingwidely separated and traveling in said chamber, a plurality of nozzlesin a wall of said ehamber each adapted to deliver fluid into the ehamberbetween a pair of vanes, and exhaust passages in a second wall of saidchamber, each of said eXhaust passages being located immediately to rearofan inlet nozzle whereby the admitted fluid forms a separating wallwhich divides the chamber into a forward portion of high pressure and arearward portion which is open to the eX- haust passage.

5. A turbine, eomprising a stator, chambers in said stator, walls tosaid chambers, a rotor, piston-vancs upon said rotor, said piston-vanesbeing widely separated and traveling in said chamber, noZzles in a wallof said chambers and adapted to deliver fluid thereinto betweenseparated vanes, and exhaust passages in a second wall of saidehainbers, each of said passages being arranged immediately to the rearof an inlet nozzle whereby the fluid admitted through said nozzle formsa separating wall which prevents the passage to eXhaust of fluid fromthe ehamber in ad- Vance of said nozzle in relation to the direction ofrotation. v

6. A turbine, comprising a stator, ebambers in said stator, walls tosaid ehambers, a rotor, piston-vanes upon said rotor, said piston-vanesbeing widely separated and traveling in said chambers, nozzles in a wallof one of said chambers adapted to deliver fluid into the chamber,passages in a second wall of said chamber, said passages leading to awall of a second of said chambers, and exhaust passages in a second walloi' said second chamber and arrangcd immediately to the rear of theinlet nozzle of that ehamber whereby the fluid forms a separating wallwhich divides the chamber into a forward portion of' high pressure and arearward portion which is open to the exhaust passage of the ehamber.

7. A turbine, comprising a stator, chambers in said stator, walls tosaid chambers, a rotor, piston-vanes upon said rotor, said piston-vanesbeing widely separated and traveling in said ehambers, nozzles in a wallof one of said chambers adapted to dcliver fluid thereinto, passages ina second wall oi" said first chamber, said passages lying immediately torear of said nozzles whereby the fluid admitted to the chamber forms aseparating wall which prevents the passage to exhaust of fluid from saidchamber in advancc of the nozzle of that chamber in relation to thedirection of rotation, said second wall of said first chamberconstituting a wall of said second of said chambers, and eXhaustpassages in a second wall of said second ehamber, said eXhaust passageslying immediately to rear of said passages whereby the fluid admitted tosaid second chamber forms a separating wall which divides the ehamberinto a forward portion of high pressure and a rearward portion which isopened to the exhaust portion of said second chamber.

S. A turbine, comprising a stator, chambers in said stator, Walls tosaid chambers, a rotor, piston-vanes upon said rotor, said piston-vanestraveling in said chambers, nozzles in a v\ all of one of said chambers,fluid delivered through said nozzles, passages in a second ?zall of saidfirstchamber, said passages lying immediately to rear of said nozzlesand leading through a v. all of a second of said chambers, secondpassages in a second v; all of said second chamber, said second passagesleading through a all of a third of said chambers, and exhaust passagesin a second 'Wall of said. third chamber, said exhaust passages lyinimmediately to rear of said second passages.

9. A turbine, comprising a stator, chambers in said stator, u'alls tosaid chambers, a rotor, piston-vanes upon said rotor, said piston-vanesbeing Widely separated and 'traveling in said chambers, nozzles in a 'uall of one of said chambers adapted to deliver 'fluid thereinto,passages in a second wall of said chambers, said second all of said'first chamber constituting a Wall of said second of said chambers,second passages in a second *a all of said second chamher, said second3-; all of said second chamber constituting a v. all of said third ofsaid chambers, and exhaust passages in a second u'all of said thirdchamber and arranged immediately to the rear of lhc inlet thereto,Whereby the fluid admitted to the chamber forms a separating Wall nhichprevents the passage to exhaust from said chamber in advance of saidnozzle in relation to the direction of rotation.

10. A turbine, comprising a stator, chambers in said stator, nalls tosaid chambers, a rotor, piston-vanes upon said rotor, said piston-vanestraveling in said chambers, nozzles in a vrall of one of said chambeis`fluid delivered through said nozzles, passages in a second Wall of saidfirst chamber, said passages l ying immediately to rear of said nozzles,said second u all of said first chamber constituting a v. all of asecond of said chambers, second passages in a second v. all of saidsecond chamber, said second passages lying immediately to rear of saidpassages, said seoond rrall of said second chamber constituting a Wallof a third of said chambers, and ex haust passages in a second `(call ofsaid third chamber, said exhaust passages lying immediately to rear ofsaid second passages.

11. A turbine, conprising a stator, Cham-- bers in said stator, v. allsto said chambers, a rotor, piston-vanes upon said rotor, saidpiston-vanes being v idely separated and traveling in said chambers,nozzles in a u. all of one of said. chambers, passages for the exit offluid from said chambers said passages being arranged immediately torear of a corresponding inlet nozzle, reversing nozzles in a Wall oi'the last of said. chambers and arranged immediately in rear of said exitpassages whereby the fluid is delivered by the reversing nozzles in adirection opposite to said nozzles in said first chamber.

12. A turbine, con'prising a stator, chambers in said stator, Walls tosaid chambers, a rotor, piston-vanes upon said rotor, said piston-vanesbeing rridely separated and traveling in said cliambers, nozzles in aWall of one of said chamhers, passages in a second Wall of said firstchamber and leading through a Wall of a second of said chambers, secondpassages in a rrall of said second chamber and leading through a vrallof 'a third of said chambers, exhaust passages in a second Wall of thethird chamber, and reversing nozzles in a vjall of a fourth of saidchambers and arranged immediately in rear oi the eXhaust passages ofthat chamber.

13. A turbine, comprising a stator, chambers in said stator, &ralle tosaid chambers, a rotor, piston-vanes, upon said rotor, said piston-vanestraveling in said chambers, nozzles in a r; all of one of said chambers,passages in a second v\ all of said first chamber, said passages lyingimmediately to rear of said nozzles and leading through a 'Wall of asecond of said chambers, second passages in a second v; all of saidsecond chamber, said second passages lying immediately to rear of saidpassages and leading through a Wall of a third of said chambers, exhaustpassages in a second 'wall of said third chamber, said exhaust passageslying immediately to rear of said second passages, reversing nozzles ina vjall of a l ourth of said chanbers, 'fluid delivered by saidreversing nozzles and exhaust passages in a second rrall of said fourthchamber, said exhaust passages lying immediately in front of saidreversing nozzles.

1.4. A turbine, comprising a stator, chambers in said stator, valls tosaid chambers, a rotor, piston-vanes upon said rotor, said piston-vanestraveling in said chambers, nozzles in a wall of one of said chambers,passages in a second v: all of said first chamber, said passages leadingthrough a all of a second of said chambers, second passages in a secondv. all of said second chamber, said second passages leading through arrall of a third of said chambers, exhaust passages in a second wall ofsaid third chamber, reversin'g nozzles in a Wall of the fourth. of saidchambers, fluid delivered. by said reversing nozzles, and passages in asecond 'wall of said fourth chamber, said second 'Wall of said fourthchamber constituting a third v: all of said third chamber.

15. A tu'bine, comprising a stator, concentric chambers in said stator,Walls to said chambers, a rotor, piston-vanes upon said rotor, saidpiston-vanes being Widely separated and traveling in said chambers,nozzles in the outer Wall of the outermost of said chambers, fluiddelivered through said nozzles, passages in the Wall between saidoutermost and the second of said chambers,

second passage/s in the wall between said second and the third of saidchambers, and exhaust passages in a second wall oi' said third chamber,said fluid forming a separating wall dividing said chamber into aforward portion of high pressure and a rearward portion open to saideXhaust passage.

16. A turbine, comprising a stator, concentric chambers in said stator,walls to said chambers, a rotor, piston-vanes upon said rotor, saidpiston-vanes traveling in said chambers, nozzles in the outer wall ofthe outermost oi' said chambers, fluid delivered through said nozzles,passages in the wall between said outermost and 'the second of saidchambers, said passagos lying immediately to rear of said nozzles,second passages in the wall between said second and the third of saidchambers, said second passages lying immediately to rear of saidpasages, and eXhaust passages in a second wall of said third chamber,said exhaust passages lying innnediatel r to rear of said secondpassages.

17. A turbine, comprising a stator, concentric chambers in said stator,walls to said chambers, a rotor, piston-vanes upon said rotor, saidpiston-vanes traveling in said chambers, nozzles in the outer wall ofthe outermost of said chambers, passages in the wall between saidoutermost and the second of said chambers, said passages lyingimmediately to rear of said nozzles, second passages in the wall betweensaid second and the third of said chambers, said second passages lyingimmediately to rear of said passages, eXhaust passages in a secondwallof said third chamber, said exhaust passages lying immediately torear of said second passages, reversing nozzles in the inner wall of theinnermost of said chambers, fluid delivered by said reversing nozzles,and eX- haust passages in a second wall of said innermost chamber lyingimmediately in front of said reversing nozzles,

18. A turbine, comprising a stator, con- `centric chambers in saidstator, said chamin a second wall of said third chamber of each series,reversing nozzles in the inner wall of each innermost chamber, fluiddelivered by said reversing nozzles, and eX- haust passages in a secondwall of each said innermost chamber.

19. A turbine, comprising a stator, concentric chambers in said stator,said chambers being in two symmetrical series, Walls to said chambers, arotor, piston-vanes arranged symmetrically upon either side of saidrotor, said piston-vanes traveling in said chambers, nozzles in theouter wall of each outermost chamber, fluid delivered through saidnozzles, passages in the wall between the outermost and the second ofeach series of chambers, said passages lying immediately to rear of saidnozzles, second passages in the wall between the second and the third ofeach series of chambers, said second passages lying immediately to rear'of said passages, and exhaust passages in a second wall of the thirdchamber in each series, said eXhaust passages lying immediately to rearof said second passages.

20. A turbine, comprising a stator, concentric chambers in said stator,said chambers being in two symmetrical series, walls to said chambers, arotor, piston-vanes arranged symmetrically upon either side of saidrotor, said piston-vanes traveling in said chambers, nozzles in theouter wall of each outermost chamber, passages in the wall between theoutermost and the second of each series of chambers, said passages lyingimmediately to rear of said nozzles, second passages in the wall betweenthe second and the third of each series of chambers, said secondpassages lyingimmediately to rear of said passages, eXhaust passages ina second wall of said third chamber of each series, said eXhaustpassages lying immediately to rear of said second passages, reversingnozzles in the inner wall of each innermost chamber, fluid delivered bysaid reversing nozzles, and eXhaust passages in a second wall of eachsaid innermost chamber lying immediately to rear of said reversingnozzles.

In witness whereof, I have hereunto set my hand in presence of twowitnesses.

ANNIBAL .TEAN BAPTISTE LG.

Witnesses:

VICTOR F. FEENY, H. D. JAMEsoN.

